Vanes Patents (Class 415/191)
  • Patent number: 11401816
    Abstract: A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, or Table IV. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.
    Type: Grant
    Filed: April 30, 2021
    Date of Patent: August 2, 2022
    Assignee: General Electric Company
    Inventors: Paul G. Deivernois, Lauren Alexandra Schuhle, Michael James Dutka, Venkata Siva Prasad Chaluvadi, Corey Lynn Hubbert, Timothy E. Dejoris, Marcus Edward Blohm, Jeremy Peter Latimer
  • Patent number: 11384640
    Abstract: A turbine rotor blade including an airfoil that extends from a platform. The platform may include a first portion of a nominal platform contour substantially in accordance with Cartesian coordinate values of X?, Y?, and Z? as set forth in Table II. The Cartesian coordinate values of X?, Y?, and Z? are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X?, Y?, and Z? by a height of the airfoil defined along a Z? axis. The X? and Y? values of the first portion are coordinate values that, when connected by smooth continuing arcs, define contour lines of the first portion of the nominal airfoil profile at each Z? coordinate value. The contour lines may be joined smoothly with one another to form the first portion.
    Type: Grant
    Filed: November 26, 2018
    Date of Patent: July 12, 2022
    Assignee: General Electric Company
    Inventors: Jalindar Appa Walunj, Sylvain Pierre, Prem Venugopal
  • Patent number: 11377961
    Abstract: An airfoil profile for a second stage turbine nozzle of a gas turbine is provided. The turbine nozzle may include an airfoil portion having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil profile sections at each Z distance, and the plurality of airfoil profile sections, when joined together by smooth continuous arcs, define an airfoil shape.
    Type: Grant
    Filed: July 16, 2021
    Date of Patent: July 5, 2022
    Inventors: Jinuk Kim, Kwangil Kim, Jason Kopko, Jeff Greenberg, Darryl Eng, David Day
  • Patent number: 11371354
    Abstract: A rotor for a turbofan booster section associated with a fan section of a gas turbine engine includes a rotor blade having an airfoil having a leading edge, a trailing edge and a mean camber line. The airfoil has a delta inlet blade angle defined as a difference between a local inlet blade angle defined in a spanwise location, and a root inlet blade angle defined at the root. The delta inlet blade angle decreases in the spanwise direction from the root to a minimum value at greater than 10% span and from the minimum value, the delta inlet blade angle increases to the tip. The rotor includes a rotor disk coupled to the rotor blade configured to be coupled to the shaft or the fan to rotate with the shaft or the fan, respectively, at the same speed as the shaft or the fan.
    Type: Grant
    Filed: June 3, 2020
    Date of Patent: June 28, 2022
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Nick Nolcheff, John Repp, Bruce Reynolds, John Gunaraj
  • Patent number: 11326461
    Abstract: A hybrid grommet assembly for a vane comprising a body portion comprising a first lip opposite a second lip forming a slot receiver, said slot receiver configured to receive a shroud slot of a shroud; said body portion comprising a vane receiver extending from said body portion and configured to receive a vane; a fiber integral within said body portion; and a potting coupled to said grommet proximate said vane receiver, wherein said potting fills a gap between the grommet and the vane.
    Type: Grant
    Filed: September 16, 2019
    Date of Patent: May 10, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Colin G. Amadon, Thomas Freeman
  • Patent number: 11306594
    Abstract: Compressor components, such as blades and vanes, having an airfoil portion with an uncoated, nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.
    Type: Grant
    Filed: February 25, 2021
    Date of Patent: April 19, 2022
    Assignee: DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO., LTD.
    Inventors: Matthew D. Montgomery, William Brian Diggs, Jaewook Song, Jerry W. Wood, John Orosa
  • Patent number: 11300135
    Abstract: A variable stator vane includes: a stator vane body which includes a radial end surface forming a clearance between the radial end surface and an outer peripheral surface of an inner casing; a rotation shaft which is rotatable so that an angle of the stator vane body with respect to a flow direction of a main stream of a working fluid is varied and which is connected to the radial end surface; and a curved surface portion which is formed on a vane surface adjacent to the radial end surface protruding radially outward from a circumference of the rotation shaft. A curvature radius of the curved surface portion is gradually decreased with distance away from the rotation shaft.
    Type: Grant
    Filed: December 5, 2018
    Date of Patent: April 12, 2022
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Satoshi Yamashita, Ryosuke Mito
  • Patent number: 11300004
    Abstract: A guide vane arrangement for a turbomachine, wherein the guide vane arrangement has a plurality of adjustable guide vanes that are rotatably mounted around an adjustment axis, at least one inner ring segment that is formed separately from the guide vanes, and a seal carrier that is formed separately from the at least one inner ring segment, wherein the at least one inner ring segment is fastened to one guide vane or to a plurality of guide vanes, and wherein the seal carrier is mounted in a spoke-centered manner with respect to the at least one inner ring segment, so that the seal carrier is movably mounted with respect to the at least one inner ring segment in the direction of at least one adjustment axis of at least one guide vane.
    Type: Grant
    Filed: August 16, 2019
    Date of Patent: April 12, 2022
    Assignee: MTU Aero Engines AG
    Inventor: Frank Stiehler
  • Patent number: 11255346
    Abstract: A fan (radial or axial fan), with an impeller and with a preguide device in the flow path in front of the impeller, preferably in front of the inlet region of an inlet nozzle, has the preguide device as a preguide grid with webs and/or guide vanes which are arranged and shaped such that flow influencing in the circumferential direction occurs for a substantially swirl-free inflow.
    Type: Grant
    Filed: May 22, 2018
    Date of Patent: February 22, 2022
    Assignee: ZIEHL-ABEGG SE
    Inventor: Frieder Loercher
  • Patent number: 11230939
    Abstract: A vane seal system includes a first non-rotatable vane segment that has a first airfoil with a first pocket at one end thereof. A second non-rotatable vane segment includes a second airfoil with a second pocket at one end thereof spaced by a gap from the first pocket. A seal member spans across the gap and extends in the first pocket and the second pocket. The seal member includes a seal element and at least one spring portion configured to positively locate the seal member in a sealing direction. Also disclosed is a seal for a vane seal system and a method related thereto for damping relative movement between a first pocket and a second pocket.
    Type: Grant
    Filed: August 10, 2020
    Date of Patent: January 25, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Mark J. Rogers, Carl S. Richardson, Richard K. Hayford, Kenneth E. Carman, Jonathan J. Earl
  • Patent number: 11225976
    Abstract: The invention relates to a housing (1) for a fluid machine, in particular for a radial fan (2), comprising at least one housing part (3), wherein the housing part (3) has at least one inlet opening (7), wherein the housing part (3) can at least partially delimit a fluid chamber (8) for receiving at least one fan wheel (9), and wherein the inlet opening (7), at least in part, has a curved inlet surface (11).
    Type: Grant
    Filed: July 2, 2018
    Date of Patent: January 18, 2022
    Assignee: KA Group AG
    Inventors: Florian Weinzierl, Dumitru-Cristian Leu, Winfried Helmenstein
  • Patent number: 11220910
    Abstract: A stator that has vanes extending between a first end and a second end along a span and from a leading edge to a trailing edge along a chord length, the vanes having a first end portion extending from the first end to about 30% of the span to a first location, a chord ratio of the chord length at the first end to the chord length at the first location greater than or equal to 1.1, a throat ratio of a width of a throat between two adjacent vanes at the first location to a width of the throat at the first end is greater than or equal to 1.3, a sweep angle difference between a maximum sweep angle of the leading edge along the first end portion and a minimum sweep angle of the leading edge along the first end portion is at least 15 degrees.
    Type: Grant
    Filed: July 26, 2019
    Date of Patent: January 11, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Alexandre Capron, Karan Anand, Hien Duong
  • Patent number: 11199095
    Abstract: The present application provides a turbine blade. The turbine blade includes a root section with a first curved section, a tip section with a second curved section, and number of mean sections positioned between the root section and the tip section. The mean sections each include a substantially prismatic shape.
    Type: Grant
    Filed: October 16, 2020
    Date of Patent: December 14, 2021
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Brian Robert Haller, Ivan William Mcbean
  • Patent number: 11181120
    Abstract: A rotor blade for a compressor of a gas turbine engine includes an airfoil extending from a root to a tip and having a leading edge and a trailing edge. The airfoil has a span that extends from 0% at the root to 100% at the tip and a mean camber line that extends from the leading edge to the trailing edge. The airfoil has a total camber distribution that increases from the root to a maximum value of total camber between 5% of the span and 20% of the span.
    Type: Grant
    Filed: November 21, 2018
    Date of Patent: November 23, 2021
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Nick Nolcheff, Jeffrey Hayes, John A. Gunaraj, Yoseph Gebre-Giorgis, David Richard Hanson, John Repp
  • Patent number: 11181003
    Abstract: A first-stage turbine vane supporting structure reduces chordal leakage between a first-stage turbine vane segment and its supporting ring. The structure includes a first-stage turbine vane segment including an outer platform, an inner platform, and a first-stage turbine vane disposed between the inner and outer platforms; an inner rail protruding from the inner platform in a longitudinal direction of the first-stage turbine vane; a supporting ring for supporting the first-stage turbine vane segment by engaging with the inner rail while facing one surface of the inner rail; a supporting member engaging with the supporting ring to define a U-shaped space bordered by three side surfaces surrounding the inner rail; and a flexible member interposed between the inner rail and one of the three side surfaces of the U-shaped space. A protrusion formed on the inner rail engages with a sealing surface of the supporting ring in an airtight manner.
    Type: Grant
    Filed: November 5, 2018
    Date of Patent: November 23, 2021
    Inventor: Dong Hwa Kim
  • Patent number: 11174203
    Abstract: A method of manufacturing a ceramic matrix composite (CMC) turbine nozzle shell is provided. The method includes: assembling a primary outer nozzle platform, a primary inner nozzle platform, a core and trailing edge preform, and an airfoil-shaped body; joining the primary outer nozzle platform to a secondary outer nozzle platform of the airfoil-shaped body; and joining the primary inner nozzle platform to a secondary inner nozzle platform of the airfoil-shaped body. Composite plies circumferentially surround the airfoil-shaped body, and their longitudinal edges are cut into fingers that are folded down. The fingers are interleaved between secondary platform plies to form the secondary outer and inner nozzle platforms.
    Type: Grant
    Filed: October 25, 2018
    Date of Patent: November 16, 2021
    Assignee: General Electric Company
    Inventors: Peter de Diego, John Ellington Greene, David Randall Hobart, James Joseph Murray, III
  • Patent number: 11125101
    Abstract: A sealing ring for a turbomachine, in particular a compressor or turbine stage of a gas turbine is provided, the sealing ring having an, in particular at least partially honeycomb-like and/or integral, seal, in particular an abradable coating (13); a profile cross section of the sealing ring, which is in particular at least partially manufactured by a generative manufacturing process, varying in the circumferential direction, in particular at least in some regions continuously and/or non-continuously at one or more circumferential positions, in particular separation points.
    Type: Grant
    Filed: June 26, 2018
    Date of Patent: September 21, 2021
    Assignee: MTU Aero Engines AG
    Inventors: Christian Scherer, Peter Eibelshaeuser, Steffen Schlothauer, Andreas Jakimov, Juergen Kraus
  • Patent number: 11116959
    Abstract: Mechanical circulatory supports configured to operate in series with the native heart are disclosed. In an embodiment, an intravascular propeller is installed into the descending aorta and anchored within via an expandable anchoring mechanism. The propeller and anchoring mechanism may be foldable so as to be percutaneously deliverable to the aorta. The propeller may have foldable blades. The blades may be magnetic and may be driven by a concentric electromagnetic stator circumferentially outside the magnetic blades. The stator may be intravascular or may be configured to be installed around the outer circumference of the blood vessel. The support may create a pressure rise between about 20-50 mmHg, and maintain a flow rate of about 5 L/min. The support may have one or more pairs of contra-rotating propellers to modulate the tangential velocity of the blood flow. The support may have static pre-swirlers and or de-swirlers.
    Type: Grant
    Filed: April 3, 2019
    Date of Patent: September 14, 2021
    Inventors: Theodosios Alexander, Martin T. Rothman
  • Patent number: 11078882
    Abstract: A runner for a hydraulic turbine configured to reduce fish mortality. The runner includes a hub and a plurality of blades extending from the hub. Each blade includes a root connected to the hub and a tip opposite the root. Each blade further includes a leading edge opposite a trailing edge, and a ratio of a thickness of the leading edge to a diameter of the runner can range from about 0.06 to about 0.35. Further, each blade has a leading edge that is curved relative to a radial axis of the runner.
    Type: Grant
    Filed: August 11, 2020
    Date of Patent: August 3, 2021
    Assignee: Natel Energy, Inc.
    Inventors: Abraham D. Schneider, Sterling Marina Watson
  • Patent number: 11066934
    Abstract: The present application provides a turbine rotor blade including an airfoil shape and a trailing edge shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, while the trailing edge profile is defined by Table II. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in the unit of distance (e.g., inches). The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.
    Type: Grant
    Filed: March 20, 2020
    Date of Patent: July 20, 2021
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Alexander Stein, Mark Steven Honkomp, Mehmet Suleyman Ciray
  • Patent number: 11028822
    Abstract: A wind turbine comprises a nacelle, a drive shaft extending from the nacelle along a shaft axis, a plurality of turbine blades coupled to the drive shaft and extending radially relative to the shaft axis, and a first static airfoil structure coupled to the wind turbine to influence airflow exiting the plurality of turbine blades. A method of increasing wind turbine efficiency in a wind farm comprises positioning a first wind turbine having a first plurality of turbine blades at least partially upstream of a second wind turbine having a second plurality of turbine blades, producing a wake field of exit air behind the first plurality of turbine blades, directing air outside of the wake field into the wake field to increase speed of airflow in the wake field, and directing the airflow into the second plurality of turbine blades of the second wind turbine.
    Type: Grant
    Filed: February 28, 2019
    Date of Patent: June 8, 2021
    Assignee: University of Massachusetts
    Inventors: Shujaut Bader, Blair Perot
  • Patent number: 11022087
    Abstract: The double-regulated turbine comprises a spherical hub, adapted to rotate around a first rotation axis, and blades, which are each able to be swivelled relative to the hub around a second rotation axis, transversal to the first rotation axis, by respective coupling flanges that are mounted fixedly on the spherical hub and that include each an attachment surface for a corresponding blade. The attachment surface of the coupling flanges includes a flat portion.
    Type: Grant
    Filed: April 17, 2015
    Date of Patent: June 1, 2021
    Assignee: Alstom Renewable Technologies
    Inventor: Hai Trieu Phan
  • Patent number: 11002293
    Abstract: A compressor rotor for a gas turbine engine includes a hub disposed about an axis of rotation and an outer surface forming a radially inner gaspath boundary, the outer surface defining a nominal hub diameter. A circumferential array of blades extends radially outwardly from the hub. A first inter-blade passage is defined between a first set of adjacent blades and has a first throat area. A second inter-blade passage is defined between a second set of adjacent blades and has a second throat area that is smaller than the first throat area. At least one scoop is disposed in the second inter-blade passage, the scoop defining a cavity extending radially into the outer surface of the hub relative to the nominal hub diameter.
    Type: Grant
    Filed: September 15, 2017
    Date of Patent: May 11, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Karan Anand, Farid Abrari, Ernest Adique, Paul Aitchison, Daniel Fudge, Kari Heikurinen, Paul Stone, Tibor Urac, Thomas Veitch
  • Patent number: 10968777
    Abstract: A vane for a gas turbine engine includes at least one airfoil. A first platform has a first rail located at a first end of the airfoil. A second platform has a second rail located at a second end of the airfoil. A first chordal seal is located on an axially aft surface of the first rail. A second chordal seal is located on an aft surface of the second rail and has a second radius of curvature at least partially truncated by an outer edge of the second rail.
    Type: Grant
    Filed: April 24, 2019
    Date of Patent: April 6, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Tracy A. Propheter-Hinckley, Kyle J. Brevick
  • Patent number: 10934870
    Abstract: The present disclosure is related to turbine vane assemblies comprising ceramic matrix composite materials. The turbine vane assemblies further including reinforcements that strengthen joints in the turbine vane assemblies.
    Type: Grant
    Filed: September 17, 2018
    Date of Patent: March 2, 2021
    Assignees: Rolls Royce Corporation
    Inventors: Michael J. Whittle, Daniel K. Vetters, Jeffrey A. Walston, Eric Koenig
  • Patent number: 10837316
    Abstract: A strut shield collar can include: a tubular portion including a tubular inside surface and a tubular outside surface; a flange portion extended from the tubular portion toward an outside of the tubular portion and including a flange inside surface; and a grid type mesh formed on at least one of the tubular inside surface and the flange inside surface, wherein the grid type mesh comprises a groove portion and a rib portion, and the groove portion is thinner than the rib portion.
    Type: Grant
    Filed: April 24, 2018
    Date of Patent: November 17, 2020
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventor: Chad Garner
  • Patent number: 10837298
    Abstract: A turbine nozzle having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, and within an envelope of approximately +/?0.049 inches, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form the airfoil shape. The X and Y values may also be scaled as a function of a first constant and the Z values may be scaled as a function of a second constant.
    Type: Grant
    Filed: August 21, 2018
    Date of Patent: November 17, 2020
    Assignee: Chromalloy Gas Turbine LLC
    Inventors: David G. Parker, Zhenhua Xiao, Richard Yu, Vincent C. Martling, Mariano Medrano, Jr., Charles A. Ellis
  • Patent number: 10823178
    Abstract: A radial compressor, with a rotor-side impeller, a stator-side housing, an inflow passage via which medium to be compressed can be fed to the impeller in the axial direction, a diffuser via which compressed medium can be conducted in the radial direction away from the impeller in the direction of a spiral housing section of the housing The diffuser radially outside in a transition region to the spiral housing section has an enlarging flow cross section.
    Type: Grant
    Filed: November 21, 2018
    Date of Patent: November 3, 2020
    Assignee: MAN Energy Solutions SE
    Inventors: Andreas Lesser, Hannes Benetschik, Christoph Heinz
  • Patent number: 10823083
    Abstract: An epicyclic gearbox includes a sun gear assembly, a planet gear assembly, and a ring gear assembly engaged with a forward planet gear and an aft planet gear of the planet gear assembly. A first axial shroud is also provided positioned forward of the forward planet gear or aft of the aft planet gear along an axial direction. The first axial shroud covers substantially all of a forward side of the forward planet gear or an aft side of the aft planet gear. The planet gear assembly is coupled to a planet gear carrier, the planet gear carrier including a radial shroud including one or more radial shroud surfaces extending along at least a portion of an outer circumference of the forward planet gear and along at least a portion of an outer circumference of the aft planet gear.
    Type: Grant
    Filed: October 18, 2018
    Date of Patent: November 3, 2020
    Assignee: GE Avio S.r.l.
    Inventor: Michele Gravina
  • Patent number: 10815811
    Abstract: A rotatable component for a turbomachine and a method for regulating a circumferential ingress of a fluid at a trailing edge of the rotatable component are disclosed. The rotatable component includes an airfoil and a mechanical component. The airfoil includes a pressure side and a suction side. The mechanical component is coupled to the airfoil and includes a forward overhanging portion, and an aft overhanging portion. The forward overhanging portion is disposed at a leading edge of the airfoil and extends longitudinally beyond the leading edge. The aft overhanging portion is disposed at a trailing edge of the airfoil and extends longitudinally beyond the trailing edge, where both the forward and aft overhanging portions further extend circumferentially along the pressure side and the suction side of the airfoil. The aft overhanging portion includes a non-axisymmetric profile for regulating the circumferential ingress of the fluid from the pressure to suction sides.
    Type: Grant
    Filed: November 28, 2017
    Date of Patent: October 27, 2020
    Assignee: General Electric Company
    Inventors: Ganesh Seshadri, Mahendran Manoharan
  • Patent number: 10808563
    Abstract: A vane seal system includes a first non-rotatable vane segment that has a first airfoil with a first pocket at one end thereof. A second non-rotatable vane segment includes a second airfoil with a second pocket at one end thereof spaced by a gap from the first pocket. A seal member spans across the gap and extends in the first pocket and the second pocket. The seal member includes a seal element and at least one spring portion configured to positively locate the seal member in a sealing direction. Also disclosed is a seal for a vane seal system and a method related thereto for damping relative movement between a first pocket and a second pocket.
    Type: Grant
    Filed: September 9, 2014
    Date of Patent: October 20, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Mark J. Rogers, Carl S. Richardson, Richard K. Hayford, Kenneth E. Carman, Jonathan J. Earl
  • Patent number: 10774650
    Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from the radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A curvature inflection point is located between 30% and 70% of an axial chord length of the airfoil.
    Type: Grant
    Filed: October 12, 2017
    Date of Patent: September 15, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Timothy Charles Nash, Thomas J. Praisner
  • Patent number: 10760425
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 27, 2018
    Date of Patent: September 1, 2020
    Assignee: General Electric Company
    Inventors: Veera Venkata Naga Krishna Satish Koyyalamudi, Matthew John McKeever, Kevin Michael Barnett
  • Patent number: 10751958
    Abstract: A composite woven outlet guide vane (32) and method of forming are depicted. The guide vane (32) is formed by use of a preform structure (100) with a core (150) which is removed following the manufacture.
    Type: Grant
    Filed: May 8, 2014
    Date of Patent: August 25, 2020
    Assignee: General Electric Company
    Inventors: Nicholas Joseph Kray, Mark Ernest Vermilyea
  • Patent number: 10711615
    Abstract: A turbine blade having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form an airfoil shape. The X and Y values may also be scaled as a function of a first constant and the Z values may be scaled as a function of a second constant.
    Type: Grant
    Filed: August 21, 2018
    Date of Patent: July 14, 2020
    Assignee: Chromalloy Gas Turbine LLC
    Inventors: David G. Parker, Zhenhua Xiao, Richard Yu, Vincent C. Martling, Wesley Smith, David Medrano, Charles A. Ellis
  • Patent number: 10704393
    Abstract: Disclosed is an airfoil array segment (110, 120, 130, 140, 150) of an airfoil array for a turbomachine, the airfoil array segment including a platform (10) having a platform surface, as well as at least two airfoils (20, 30). The platform surface has a depression (111, 121, 131, 141, 151) which extends up to the first airfoil and contacts the pressure side (21) of the first airfoil downstream of 80% of the axial chord (g) downstream of the leading edges (23, 33) and which contacts the pressure side (21) of the first airfoil downstream up to no more than 80% of the axial chord (g) downstream of the leading edges (23, 33). At least one lowest point (112, 122) of the depression is located at least 90% of the axial chord (g) downstream of the leading edges (23, 33). Also disclosed are an airfoil array, an airfoil passage, a platform, a turbomachine, and an aircraft engine.
    Type: Grant
    Filed: May 9, 2018
    Date of Patent: July 7, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Fadi Maatouk, Markus Brettschneider, Inga Mahle
  • Patent number: 10689996
    Abstract: A turbomachine blade (10) comprising a body (11) and an elastomer gasket (12) fastened to said body (11).
    Type: Grant
    Filed: June 16, 2017
    Date of Patent: June 23, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Gilles Pierre-Marie Notarianni, Audrey Laguerre, Stephane Roger Mahias
  • Patent number: 10655502
    Abstract: A stator assembly of a gas turbine engine according to an example of the present disclosure includes, among other things, a first shroud extending about an axis to bound a flow path. The first shroud defines a first shroud opening. An airfoil has an airfoil body extending from a first end portion. The first end portion is received in the first shroud opening and defines at least one airfoil opening. At least one retention clip has an arcuate portion extending from a first elongated leg portion. The first elongated leg portion and the arcuate portion are received through the at least one airfoil opening such that the at least one retention clip limits movement of the airfoil relative to the first shroud.
    Type: Grant
    Filed: May 26, 2017
    Date of Patent: May 19, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brian Barainca, Gary F. Fowler
  • Patent number: 10655483
    Abstract: A guide vane segment 10 for a turbomachine includes a radially inner shroud plate 13 having a shroud plate surface 14 that is adapted to be configured in the turbomachine to face a rotor blade 20 adjacent to the guide vane segment, and thereby essentially extend along an outer conical surface K1 whose cone axis coincides with the axis of rotation A of a rotor shaft 30. In a radially inner region, a rotor blade 20 for a turbomachine has a base plate 23 having a base plate surface 24 that is adapted to be configured in the turbomachine to face a shroud of a guide vane row 10 adjacent to the rotor blade and thereby essentially extend along an outer conical surface K2 whose cone axis coincides with the axis of rotation A of a rotor shaft 30.
    Type: Grant
    Filed: December 1, 2016
    Date of Patent: May 19, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Martin Pernleitner, Manfred Dopfer, Marcus Woehler, Oliver Thiele, Bernd Kislinger, Norman Cleesattel, Christoph Lauer, Manfred Schill, Manuel Hein
  • Patent number: 10633989
    Abstract: A nozzle has an airfoil, and the nozzle is configured for use with a turbomachine. The airfoil has a throat distribution measured at a narrowest region in a pathway between adjacent nozzles, at which adjacent nozzles extend across the pathway between opposing walls to aerodynamically interact with a fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on the airfoil. A trailing edge of the airfoil deviates from an axial plane by about 0.1 degrees to about 5 degrees. A turbomachine comprising a plurality of nozzles is also provided.
    Type: Grant
    Filed: December 18, 2015
    Date of Patent: April 28, 2020
    Assignee: General Electric Company
    Inventors: Shashwat Swami Jaiswal, Rohit Chouhan, Lukasz Szajko
  • Patent number: 10619496
    Abstract: A turbine vane has an airfoil extending between an inner platform and an outer platform. The airfoil is hollow. A hollow within the airfoil extends between an inner leading edge to an inner trailing edge. An inner radius is defined at the inner trailing edge in a circumferential direction measured between walls which extend from the inner leading edge to the inner trailing edge. The inner radius varies along a radial length defined between the inner and outer platforms. A mid-turbine frame and a gas turbine engine are also disclosed.
    Type: Grant
    Filed: May 20, 2014
    Date of Patent: April 14, 2020
    Assignee: United Technologies Corporation
    Inventors: Steven D. Porter, John T. Ols
  • Patent number: 10619497
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: May 10, 2018
    Date of Patent: April 14, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Pascal Pierre Nicolas Routier, Jean-Armand Marc Emilien Destouches, Thomas Michel Julien Mervant, Ludovic Pintat, Guillaume Jochen Scholl
  • Patent number: 10612563
    Abstract: An air conditioner comprises a compressor to compress a refrigerant, a heat exchanger to move heat of the refrigerant, and a blower to blow air. The blower comprises a fan rotatable about a rotation axis, and a plurality of stationary blades installed to be a radial shape about the rotation axis in a direction in which the airflow generated by the rotation of the fan is discharged, and are curved in a direction opposite to the rotation direction of the fan from an inner circumferential portion to an outer circumferential portion. The stationary blades comprise an inlet edge, and an outlet edge, and an inlet angle formed by the inlet edge and the rotation axis and a chord angle formed by a chord connecting the inlet edge and the outlet edge and the rotation axis are larger at the inner and outer circumferential portions than at a radial center portion.
    Type: Grant
    Filed: July 10, 2015
    Date of Patent: April 7, 2020
    Assignee: SAMSUNG ELECTRONICS CO., LTD.
    Inventor: Seiji Sato
  • Patent number: 10590954
    Abstract: The invention relates to a flow-conducting grille designed as a pre-conducting grille for arranging on a suction region of a fan, wherein the flow-conducting grille has a grille web structure about an axial center line, which grille web structure comprises radial webs spaced apart in the circumferential direction and coaxial circumferential webs spaced apart in the radial direction and an outer ring, wherein an inflow side of the flow-conducting grille extends flat and parallel to a radial plane of the flow-conducting grille.
    Type: Grant
    Filed: May 19, 2016
    Date of Patent: March 17, 2020
    Assignee: ebm-papst Mulfingen GmbH & Co. KG
    Inventors: Zhang Binyuan, Christian Haag, Carsten Hübner, Björn Sudler, Manuel Vogel
  • Patent number: 10590782
    Abstract: A turbine nozzle having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, and within an envelope of approximately ?0.067 to +0.101 inches, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form the airfoil shape. The X and Y values may also be scaled as a function of a first constant and the Z values may be scaled as a function of a second constant.
    Type: Grant
    Filed: August 21, 2018
    Date of Patent: March 17, 2020
    Assignee: CHROMALLOY GAS TURBINE LLC
    Inventors: David G. Parker, Zhenhua Xiao, Richard Yu, Vincent C. Martling, Paul Gregory Herber, Daniel Folkers
  • Patent number: 10583932
    Abstract: A gas turbine engine of an aircraft includes: an engine core having a turbine including a lowest pressure rotor stage, a turbine diameter, a fan including a plurality of fan blades extending from a hub, an annular fan face at a leading edge of the fan; wherein a downstream blockage ratio is: the ? ? turbine ? ? diameter ? ? at ? ? an ? ? axial location ? ? of ? ? the ? ? lowest ? ? pressure ? ? rotor ? ? stage ? ground ? ? plane ? ? to ? ? wing ? ? distance and a quasi-non-dimensional mass flow rate Q defined as: Q = W ? T ? ? 0 P ? ? 0 · A flow where: W is mass flow rate through the fan in Kg/s; T0 is average stagnation temperature of the air at the fan face in Kelvin; P0 is average stagnation pressure of the air at the fan face in Pa; and Aflow is the flow area of the fan face in m2, and wherein a Q ratio of: the downstream blockage ratio×Q is in a range from 0.005 to 0.01.
    Type: Grant
    Filed: April 30, 2019
    Date of Patent: March 10, 2020
    Assignee: ROLLS-ROYCE plc
    Inventors: Richard G Stretton, Michael C Willmot
  • Patent number: 10577953
    Abstract: A stator vane is comprised of: an airfoil section elongated in a radial direction relative to an axis; an outer band section continuous to an outer end of the airfoil section and bent in a circumferential direction relative to the axis; a first hook section continuous to a leading end in the axial direction of the outer band section and bent outward in the radial direction; a second hook section continuous to a trailing end in the axial direction of the outer band section and bent outward in the radial direction; an inner band section continuous to an inner end of the airfoil section and bent in the circumferential direction; a flange section continuous to an end in the axial direction of the inner band section and bent inward in the radial direction; and a reinforcement fiber fabric continuous throughout these sections and unitized with a ceramic.
    Type: Grant
    Filed: September 22, 2016
    Date of Patent: March 3, 2020
    Assignee: IHI Corporation
    Inventor: Fumiaki Watanabe
  • Patent number: 10577938
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: May 10, 2018
    Date of Patent: March 3, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Thomas Michel Julien Mervant, Vincent Nicolas Leonardon, Pierre Hervé Fernand Marche, Pascal Pierre Nicolas Routier, Ludovic Pintat
  • Patent number: 10577937
    Abstract: A fan blade is provided with an aerofoil portion for which, for cross-sections through the aerofoil portion at radii between 15% and 25% of the blade span from the root radius, the average leading edge thickness is greater than the leading edge thickness at the tip. The geometry of the fan blade may result in a lower susceptibility to flutter.
    Type: Grant
    Filed: February 12, 2018
    Date of Patent: March 3, 2020
    Assignee: ROLLS-ROYCE plc
    Inventors: Mark J. Wilson, Gabriel Gonzalez-Gutierrez, Marco Barale, Benedict Phelps, Kashmir S. Johal, Nigel H S Smith
  • Patent number: 10570767
    Abstract: An apparatus and method of a gas turbine engine comprising a rotor having at least one disk with a rotor defining an axial face and a stator having at least one ring with a stator axial face confronting the rotor axial face, with terminal portions of the axial faces forming a fluid outlet there between. A recess formed in one of the axial faces defines a buffer cavity into which a wing extends from the other of the axial faces and having a surface confronting the fluid outlet. A flow reverser is further provided within at least one of the surface or the terminal portion of the other of the axial faces.
    Type: Grant
    Filed: February 5, 2016
    Date of Patent: February 25, 2020
    Assignee: General Electric Company
    Inventors: Jonathan Russell Ratzlaff, Ronald Scott Bunker